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Comparison of the performance of a helicopter-type ram-jet engine under various centrifugal loadings

Description: Report presenting an investigation of an 18-foot-radius helicopter rotor powered by tip-mounted ramjet engines in the helicopter test tower. The engine performance is compared with the performance determined in a previous investigation of a 9-foot-radius rotor with the same engines at similar speeds but with twice the centrifugal forces. Results regarding the propulsive characteristics, minimum specific fuel consumption and corresponding propulsive thrust, and operational characteristics are provided.
Date: October 7, 1953
Creator: Radin, Edward J. & Carpenter, Paul J.
Partner: UNT Libraries Government Documents Department

Optimum Lifting Bodies at High Supersonic Airspeeds

Description: Memorandum presenting a determination of the shapes of bodies with minimum pressure drag for a given lift at high supersonic speeds and satisfying conditions of given length and width with the aid of Newton's law of resistance. The resulting shapes have flat bottoms which are also rectangular. To determine if the bodies do actually have improved lift-drag ratios at high supersonic speeds, several wedges satisfying numerically different sets of given conditions were tested at Mach number 5.
Date: May 7, 1954
Creator: Rosnikoff, Meyer M.
Partner: UNT Libraries Government Documents Department

Identification of Foreign Objects Damaging Compressor Blades in Turbojet Engines

Description: "Damage to the compressor blades of turbojet engines due to ingestion of foreign objects is a growing problem, the solution of which has been made more difficult by the large percentage of damaging materials that have remained unknown. A rapid emission spectroscopic method was devised to identify the chemical composition of these foreign objects. Results on laboratory-prepared specimens and blades from damaged engines show that the method can be utilized to determine the nature of the ingested foreign objects" (p. 1).
Date: January 7, 1957
Creator: Spakowski, A. E. & Graab, J.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation at Low Speed of a Wing Having 63 Degree Sweepback and a Drooped Tip

Description: From Summary: "The results of force tests made at low speed are presented to show the effect of longitudinal static stability produced by drooping the tip of a 63 degree sweptback wing. Five semispan wing models were tested: two incorporated curved drooped tips, two with abruptly drooped tips, and one without droop. The most favorable stability characteristics were measured for a model with an abruptly drooped tip, a fence, and a leading-edge flap; however, the use of these same auxiliary devices on the undrooped wing was nearly as effective."
Date: April 7, 1955
Creator: Blackaby, James R.
Partner: UNT Libraries Government Documents Department

Cooperative Investigation of Relationship Between Static and Fatigue Properties of Heat-Resistant Alloys at Elevated Temperatures

Description: Memorandum presenting a study of the relationship between the static and dynamic properties of heat-resistant alloys at high temperatures. An auxiliary objective is to provide a better basis for evaluating the results from the various types of fatigue machines.
Date: March 7, 1951
Creator: NACA Subcommittee on Heat-Resisting Materials
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of the Motion of a 1/10-Scale Model of the Douglas XF4D-1 Escape Capsule When Jettisoned by Jet Ejection: TED No. NACA DE 359

Description: Memorandum presenting a wind-tunnel investigation at low speed to determine the path and motion of a scale model of the Douglas XF4D-1 escape capsule without the drogue parachute when jettisoned by jet ejection. The investigation included determination of the vertical and horizontal accelerations of the capsule. Results regarding the ejection at zero airspeed, ejection at 570 feet per second, and at 863 feet per second are provided.
Date: October 7, 1953
Creator: Johnson, Harold S.
Partner: UNT Libraries Government Documents Department

Data From Large-Scale Low-Speed Tests of Airplane Configurations With a Thin 45 Degree Swept-Wing Incorporating Several Leading-Edge Contour Modifications

Description: Memorandum presenting force tests that have been made of airplane configurations with a thin swept wing incorporating several wing-contour modifications forward of maximum thickness. Both longitudinal and lateral characteristics are provided.
Date: May 7, 1956
Creator: Evans, William T.
Partner: UNT Libraries Government Documents Department

The Effect of Air Jets Simulating Chines or Multiple Steps on the Hydrodynamic Characteristics of a Streamline Fuselage

Description: Memorandum presenting preliminary tests in order to determine the effect of forced ventilation on the hydrodynamic characteristics of a scale model of a streamline fuselage of a hypothetical transonic airplane. The forced ventilation consisted of air ejected at about 300 feet per second through small orifices distributed over the fuselage bottom in a series of patterns simulating chines or multiple steps. Results regarding resistance, effective hydrodynamic lift, trim, spray, and air flow are provided.
Date: January 7, 1949
Creator: Weinflash, Bernard
Partner: UNT Libraries Government Documents Department

The Effects of Leading-Edge Extensions, a Trailing-Edge Extension, and a Fence on the Static Longitudinal Stability of a Wing-Fuselage-Tail Combination Having a Wing With 35 Degrees of Sweepback and an Aspect Ratio of 4.5

Description: Memorandum presenting an investigation of the leading-edge extensions, a trailing-edge extension, and a fence on the static longitudinal stability of a wing-fuselage-tail combination with a wing with 35 degrees of sweepback and an aspect ratio of 4.5. The investigation involved the use of force measurements and tuft studies on stall progression. Results regarding a model with unmodified wing, the effect of leading-edge modifications, the effects of the fence, a summary of the effects of compressibility, and some remarks on flow separation are provided.
Date: August 7, 1953
Creator: Selan, Ralph & Bandettini, Angelo
Partner: UNT Libraries Government Documents Department

Theoretical study of the tunnel-boundary lift interference due to slotted walls in the presence of the trailing-vortex system of a lifting model

Description: Report presenting some equations that give the interference on the trailing-vortex system of a uniformly loaded finite-span wing in a circular tunnel containing partly open and partly closed walls, with special reference to symmetrical arrangements of the open and closed portions. Methods are given for extending the equations to include tunnel shapes other than circular.
Date: April 7, 1953
Creator: Matthews, Clarence W.
Partner: UNT Libraries Government Documents Department

Pressure distribution at low speed on a model incorporating a W wing with aspect ratio 6, 45 degrees sweep, taper ratio 0.6, and an NACA 65A009 airfoil section

Description: Report presenting results of pressure-distribution measurements at low speed on a wing-fuselage combination with a wing of W plan form with aspect ratio 6, 45 degrees sweep, taper ratio 0.6, and an NACA 65A009 airfoil section placed parallel to the plane of symmetry. Results regarding aerodynamic characteristics, pressure distribution on the wing, pressure distribution on the fuselage, aerodynamic section characteristics, and stall patterns are provided.
Date: August 7, 1952
Creator: Polhamus, Edward C. & Few, Albert G., Jr.
Partner: UNT Libraries Government Documents Department

Preliminary investigation of combustion in flowing gas with various turbulence promoters

Description: Report presenting an investigation of combustion occurring downstream of various turbulence promoters in a 20-inch length of a 1 7/8-inch inside-diameter, water-jacketed tubing using premixed vaporized fuel and air. Among the turbulence promoters investigated were flat plates perforated with 1/8-inch diameter holes, 1/4-inch diameter holes, and a single large hole to give 12.4, 17.2, and 21.5 percent open area respectively.
Date: June 7, 1948
Creator: Haddock, Gordon W. & Childs, J. Howard
Partner: UNT Libraries Government Documents Department

An investigation of three NACA 1-series nose inlets at subsonic and transonic speeds

Description: Report presenting an investigation of three NACA 1-series nose inlets at subsonic and transonic speeds in the 8-foot transonic tunnel. Drag, surface-pressure, and pressure-recovery measurements and schileren photographs were obtained at zero angle of attack through a range of Mach numbers and mass-flow-ratios. Results regarding tunnel boundary interference, surface pressure distribution, external drag, and pressure recovery are provided.
Date: January 7, 1953
Creator: Pendley, Robert E.; Milillo, Joseph R. & Fleming, Frank F.
Partner: UNT Libraries Government Documents Department

Measurements of fluctuating pressures on a 1/4-scale model of the X-1 airplane with a 10-percent-thick wing in the Langley 16-foot transonic tunnel

Description: Report presenting pressure fluctuations measured near the trailing edge of the wing and near the leading edge of the tail of a scale model of the X-1 airplane with a 10-percent-thick wing in the 16-foot transonic tunnel. Results regarding frequency analyses are also provided.
Date: January 7, 1953
Creator: Habel, Louis W. & Steinberg, Seymour
Partner: UNT Libraries Government Documents Department

A flight investigation at transonic speeds of a model having a triangular wing of aspect ratio 2

Description: Report presenting free-falling recoverable model tests conducted at transonic speeds on a model with a triangular wing of aspect ratio 2 and a 45 degree swept tail in the chord plane of the wing. Static- and dynamic-longitudinal-stability data for the complete model, force and moment data for the major components of the model, and load distributions over the fuselage of the model were evaluated at several angles of attack.
Date: September 7, 1955
Creator: White, Maurice D.
Partner: UNT Libraries Government Documents Department

Bonded lead monoxide films as solid lubricants for temperatures up to 1250 degrees F

Description: Report presenting a friction, wear, and endurance-lift study made with bonded films of mixed oxides containing lead monoxide (PbO) as the main component. The coatings lubricated over the entire temperature range, but were far more effective from 500 to 1250 degrees Fahrenheit than at the lower temperatures. Results regarding the effect of silica additions on coating formation, determination of coating composition, effect of coating thickness on friction and wear, effect of temperature on friction and wear, and endurance properties are provided.
Date: May 7, 1957
Creator: Sliney, Harold E. & Johnson, Robert L.
Partner: UNT Libraries Government Documents Department

Longitudinal stability and control characteristics at Mach numbers of 1.41 and 2.01 of a 67 degree swept-wing airplane configuration with canard control surfaces

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41 and 2.01 to determine the stability and control characteristics of a canard-controlled airplane configuration with potentially high values of lift-drag ratio. The configurations investigated included a plane and a twisted wing with approximately 67 degrees of sweep and an aspect ratio of 2.91 and three trapezoidal canard surfaces with ratios of exposed area to wing area of 0.032, 0.076, and 0.121.
Date: July 7, 1958
Creator: Spearman, M. Leroy & Robinson, Ross B.
Partner: UNT Libraries Government Documents Department

Theoretical performance of JP-4 fuel and liquid oxygen as a rocket propellant 2: equilibrium composition

Description: Data were calculated for equivalence ratios of 1 to 3, chamber pressures of 300 and 600 pounds per square inch absolute, and pressure ratios of 1 to 1500. Parameters included are specific impulse, combustion and exit temperature, molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, isentropic exponent, viscosity, and thermal conductivity. A correlation is given which permits determination of performance for a wide range of chamber pressures.
Date: September 7, 1956
Creator: Huff, Vearl N.; Fortini, Anthony & Gordon, Sanford
Partner: UNT Libraries Government Documents Department

Initial flutter tests in the Langley transonic blowdown tunnel and comparison with free-flight flutter results

Description: Report presenting an experimental wing-flutter investigation in the transonic blowdown tunnel, which is equipped with a slotted test section, in order to determine the correlation between transonic-wind-tunnel and free-fall flight flutter results. Very good agreement was observed between wind tunnel and flight flutter test results, which showed the feasibility of conducting flutter tests in transonic wind tunnels with slotted test sections.
Date: January 7, 1953
Creator: Bursnall, William J.
Partner: UNT Libraries Government Documents Department

Free-spinning-tunnel investigation to determine the effect of spin-recovery rockets and thrust simulation on the recovery characteristics of a 1/25-scale model of the Chance Vought XF8U-1 airplane: TED No. NACA DE 392

Description: Report presenting an investigation of a model of the Chance Vought XF8U-1 airplane to determine the effect of spin-recovery rockets on the recovery characteristics of the model. The investigation also included tests to determine the effect of simulated engine thrust on the recovery characteristics of the model. Results regarding yaw rockets, thrust-simulation rocket, and roll rockets are provided.
Date: February 7, 1955
Creator: Burk, Sanger M., Jr. & Lee, Henry A.
Partner: UNT Libraries Government Documents Department

Effects of slot size and geometry on the flow in rectangular tunnels at Mach numbers up to 1.4

Description: Report presenting an investigation of the effects of slot width, depth, shape, and spacing on the center-line pressure distribution in rectangular tunnels of constant cross section with several height-to-width ratios. Results are presented in the form of center-line static-pressure distributions and calculated static-pressure and angle-of-flow distributions along the slotted boundary.
Date: April 7, 1953
Creator: Nelson, William J. & Cubbage, James M., Jr.
Partner: UNT Libraries Government Documents Department

Investigation of boundary-layer transition on flat-faced bodies of revolution at high supersonic speeds

Description: An experimental investigation was carried out to determine the boundary-layer transition characteristics of bodies of revolution with flat and nearly flat faces. Shadowgraphs indicated that the boundary layer remained laminar on the front faces and was turbulent only on the sides. The tests also yielded information on the total drag coefficients and static longitudinal stability of the models.
Date: June 7, 1957
Creator: Canning, Thomas N. & Sommer, Simon C.
Partner: UNT Libraries Government Documents Department

A study of a missile designed to fly at low speed with its longitudinal axis aligned with the flight path

Description: An experimental investigation to explore the practicability of a low-speed missile designed to fly with its longitudinal axis pointing along the flight path. The wing and tail surfaces were arranged in a cruciform pattern and the incidence was selected to trim the missile at the desired normal-force coefficient with the body at 0 degrees angle of attack. Results regarding the description of a self-balancing missile and experimental results are provided.
Date: February 7, 1956
Creator: Hopkins, Edward J. & Sorensen, Norman E.
Partner: UNT Libraries Government Documents Department